Combustor Fairing Redirects Airflow to Prevent Separation

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Solution Overview

Problem

Gas turbine engine combustors face airflow separation and particulate buildup on heat shield panels, leading to reduced cooling efficiency and potential structural damage due to excess temperatures and particulate inhibition of airflow.

Innovation Solution

Incorporating a fairing system and lateral flow injection feature in the combustor design to redirect airflow and generate a cross flow, reducing particulate accumulation on heat shield panels and improving cooling efficiency by promoting airflow parallel to the panels.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If cooling structures are used to protect combustor panels from heat, then thermal protection is improved, but airflow separation occurs and cooling efficiency deteriorates

Engineering Contradiction:

Improvethermal protectionVSAvoidcooling efficiency

Core Design Contradiction:

TemperatureVSProductivity

Solution Approach 1:

The patent applies curvature to the cooling structures by forming fairings with curved surfaces that guide airflow smoothly around the combustor panels. The fairings have rounded leading edges and curved transition surfaces that eliminate sharp corners, preventing flow separation and maintaining attached cooling airflow while still providing thermal protection to the panels.

Inventive Principle:

Principle #14Spheroidality (Curvature)

Solution Approach 2:

The fairing acts as an intermediary component between the incoming cooling airflow and the combustor panels. It mediates the airflow by shaping and directing it to flow smoothly over the panel surfaces, ensuring both thermal protection of the panels and maintained cooling efficiency through attached flow.

Inventive Principle:

Principle #24Intermediary (Mediator)

2Temperature

If cooling airflow is increased to protect structures from excess temperatures, then thermal protection is improved, but particulate buildup on panels increases and blocks cooling

Engineering Contradiction:

Improvethermal protectionVSAvoidparticulate buildup

Core Design Contradiction:

TemperatureVSObject-affected harmful factors

Solution Approach 1:

The patent replaces mechanical particulate removal systems with aerodynamic flow control. By using curved fairings to generate attached cooling flow with favorable pressure gradients, the system uses airflow mechanics itself to prevent particulate deposition, eliminating the need for additional mechanical removal mechanisms.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The patent converts the potentially harmful effect of high-velocity cooling airflow (which could carry particulates to the panels) into a beneficial effect. The curved fairings shape the airflow to create protective attached flow that actually prevents particulate deposition while maintaining the cooling function, turning a potential harm into a benefit.

Inventive Principle:

Principle #22Blessing in disguise (Convert harm into benefit)

Applied Scientific Principles

This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.

Function Achieved in This Case

The solution effectively reduces airflow separation and particulate buildup, maintaining cooling efficiency and extending the durability of heat shield panels by ensuring effective airflow and heat dissipation.

Implementation Method 1

the second surface of the first component is oriented relative to a first airflow path such that airflow in the first airflow path separates from the second surface of the first component

Methodology Applied

Scientific EffectFlow separation: Flow Separation

Implementation Method 2

a first component having a first surface and a second surface opposite the first surface, the first component including a cooling hole extending from the second surface to the first surface through the first component

Methodology Applied

Scientific EffectConvection: Convection

Data Source

PatentUS20240247613A1Apparatus and method for mitigating airflow separation around engine combustor

Publication Date: 2024.07.25 RTX CORP

AI summary

According to one embodiment, a gas turbine engine component assembly is provided. The gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, the first component including a cooling hole extending from the second surface to the first surface through the first component, wherein the second surface of the first component is oriented relative to a first airflow path such that airflow in the first airflow path separates from the second surface of the first component; and a first fairing secured to the first component proximate the second surface of the first component, the first fairing being configured to redirect airflow in the first airflow path such that the airflow exits the first fairing oriented parallel with the second surface of the first component.